[Federal Register Volume 64, Number 194 (Thursday, October 7, 1999)]
[Rules and Regulations]
[Pages 54515-54517]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25766]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-268-AD; Amendment 39-11350; AD 99-21-07]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-9, DC-9-80,
and C-9 (Military) Series Airplanes, and Model MD-88 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes two existing airworthiness
directives (AD), applicable to certain McDonnell Douglas Model DC-9,
DC-9-80, and C-9 (military) series airplanes, and Model MD-88
airplanes, that currently require installation of hydraulic line
restrictors in the main landing gear (MLG), and modification or
replacement of the left and right MLG hydraulic damper assemblies. This
amendment requires an additional modification of the MLG hydraulic
damper assemblies, or replacement of the MLG hydraulic damper
assemblies with modified and reidentified hydraulic damper assemblies.
This amendment is prompted by reports indicating that MLG hydraulic
damper assemblies removed for overhaul had failed or damaged spring
retainers, due to insufficient material thickness of the spring
retainers. The actions specified by this AD are intended to prevent
failure of the hydraulic damper assemblies of the MLG, which could
result in vibration damage and collapse of the MLG.
DATES: Effective November 12, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 12, 1999.
The incorporation by reference of McDonnell Douglas Service
Bulletin DC9-32-289, dated March 7, 1996, listed in the regulations was
approved previously by the Director of the Federal Register as of
November 14, 1996 (61 FR 53042, October 10, 1996).
The incorporation by reference of certain other publications listed
in the regulations was approved previously by the Director of the
Federal Register as of February 26, 1996 (61 FR 2407, January 26,
1996).
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Aircraft Group, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 90846. This information
may be examined at the Federal Aviation Administration (FAA), Transport
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Transport Airplane Directorate, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
California; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Albert Lam, Aerospace Engineer,
Systems and Equipment Branch, ANM-130L, FAA, Transport Airplane
Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5346;
fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 96-01-09,
amendment 39-9485 (61 FR 2407, January 26, 1996), and AD 96-21-01,
amendment 39-9777 (61 FR 53042, October 10, 1996), which are applicable
to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military)
series airplanes, and Model MD-88 airplanes, was published in the
Federal Register on July 23, 1999 (64 FR 39944). The action proposed to
require an additional modification of the main landing gear (MLG)
hydraulic damper assemblies, or replacement of the MLG hydraulic damper
assemblies with modified and reidentified hydraulic damper assemblies.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
Cost Impact
There are approximately 2,015 airplanes of the affected design in
the worldwide fleet. The FAA estimates that 1,145 airplanes of U.S.
registry will be affected by this AD.
The installation that is currently required by AD 96-01-09, and
retained in this AD, takes approximately 4 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
parts cost approximately $928 per airplane. Based on these figures, the
cost impact of the currently required installation on U.S. operators is
estimated to be $1,168 per airplane.
The modification that is currently required by AD 96-01-09, and
retained in this AD, takes approximately 6 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
parts cost approximately $4,000 per airplane. Based on these figures,
the cost impact of the currently required modification on U.S.
operators is estimated to be $4,360 per airplane.
The replacement that is currently required by AD 96-21-01, and
retained in this AD, takes approximately 6 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
parts cost approximately $11,139 per airplane (two assemblies at $5,569
each). Based on these figures, the cost impact of the currently
required replacement on U.S. operators is estimated to be $11,499 per
airplane.
The modification that is currently required by AD 96-21-01, and
retained in this AD, takes approximately 11 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
parts cost approximately $2,907 per airplane. Based on these figures,
the cost impact of the currently required modification on U.S.
operators is estimated to be $3,567 per airplane.
The modification or replacement that is required in this AD action
will take approximately 18 work hours per airplane to accomplish, at an
average labor rate of $60 per work hour. Required parts will cost
approximately $608 per airplane. Based on these figures, the cost
impact of the modification required by this AD on
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U.S. operators is estimated to be $1,932,760, or $1,688 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
AD action, and that no operator would accomplish those actions in the
future if this AD were not adopted.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) Is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-9485 (61 FR
2407, January 26, 1996), and amendment 39-9777 (61 FR 53042, October
10, 1996), and by adding a new airworthiness directive (AD), amendment
39-11350, to read as follows:
99-21-07 McDonnell Douglas: Amendment 39-11350. Docket 98-NM-268-
AD. Supersedes AD 96-01-09, Amendment 39-9485; and AD 96-21-01,
Amendment 39-9777.
Applicability: Model DC-9-81 (MD-81), -82 (MD-82), -83 (MD-83),
and 87 (MD-87) series airplanes, and Model MD-88 airplanes; as
listed in McDonnell Douglas Service Bulletins MD80-32-276 and MD80-
32-278, both dated March 31, 1995; and Model DC-9-10, -20, -30, -40,
and -50; and C-9 (military) series airplanes, as listed in McDonnell
Douglas Service Bulletin DC9-32-289, dated March 7, 1996;
certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (h) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the hydraulic damper assemblies of the
MLG, which could result in vibration damage and collapse of the MLG,
accomplish the following:
Restatement of Requirements of AD 96-01-09
Modifications
(a) For airplanes listed in McDonnell Douglas MD-80 Service
Bulletin MD80-32-276, dated March 31, 1995, that have not been
previously modified (installation of brake line restrictors) in
accordance with McDonnell Douglas MD-80 Service Bulletin MD80-32-
246: Within 9 months after February 26, 1996 (the effective date of
AD 96-01-09, amendment 39-9485), install filtered brake line
restrictors in the MLG hydraulic brake system in accordance with
McDonnell Douglas MD-80 Service Bulletin MD80-32-276, dated March
31, 1995, or Revision 1, dated October 17, 1995.
Note 2: Installation of filtered restrictors in accordance with
the instructions specified in McDonnell Douglas MD-80 Alert Service
Bulletin, MD80-A32-286, dated September 11, 1995, is considered
acceptable for compliance with paragraph (a) of this AD.
(b) For airplanes listed in McDonnell Douglas MD-80 Service
Bulletin MD80-32-278, dated March 31, 1995: Within 36 months after
February 26, 1996, modify the hydraulic damper assembly (by removing
shims, increasing bolt torque, and incorporating changes to increase
the volume of fluid passing between the two damper chambers) in
accordance with McDonnell Douglas MD-80 Service Bulletin MD80-32-
278, dated March 31, 1995, or Revision 1, dated September 6, 1995.
Restatement of Requirements of AD 96-21-01
Replacement or Modification
(c) For airplanes listed in McDonnell Douglas Service Bulletin
DC9-32-289, dated March 7, 1996: Within 24 months after November 14,
1996 (the effective date of AD 96-21-01, amendment 39-9777), either
replace or modify the MLG hydraulic damper assembly, in accordance
with the procedures specified as either ``Option 1'' or ``Option
2,'' respectively, of the service bulletin.
New Requirements of this Ad
Replacement or Modification
(d) For McDonnell Douglas Model DC-9 series airplanes, and C-9
(military) series airplanes (as listed in McDonnell Douglas Alert
Service Bulletin DC9-32A311, Revision 01): Within 18 months after
the effective date of this AD, accomplish the requirements specified
in either paragraph (d)(1) or (d)(2) of this AD in accordance with
McDonnell Douglas Service Bulletin DC9-32-311, dated July 6, 1998,
or McDonnell Douglas Alert Service Bulletin DC9-32A311, Revision 01,
dated March 8, 1999.
(1) Modify the left and right MLG hydraulic damper assemblies.
(2) Replace the left and right MLG hydraulic damper assemblies
with modified and reidentified hydraulic damper assemblies having
part number (P/N) SR09320057-7005, SR09320057-7007, SR09320057-7009,
or 5923142-5513.
(e) For McDonnell Douglas Model DC-9-80 series airplanes, and
MD-88 airplanes (as listed in McDonnell Douglas Alert Service
Bulletin DC9-32A311, Revision 01): Within 3,000 flight cycles after
incorporation of the latest configuration of the left and right MLG
hydraulic damper assemblies, or within 9 months after the effective
date of this AD, whichever occurs later; accomplish the requirements
specified in either paragraph (d)(1) or (d)(2) of this AD in
accordance with McDonnell Douglas Service Bulletin DC9-32-311, dated
July 6, 1998, or McDonnell Douglas Alert Service Bulletin DC9-
32A311, Revision 01, dated March 8, 1999.
(f) Paragraph (b) or (c) of this AD, as applicable, must be
accomplished prior to or concurrent with the accomplishment of
either paragraph (d) or (e) of this AD, as applicable.
Spares
(g) As of the effective date of this AD, no person shall install
on any airplane a damper sub assembly having P/N SR09320057-9,
SR09320057-17, or 5923142-5017; or a damper assembly having P/N
SR09320057-7001, SR09320057-7003, or 5923142-5511, unless the part
has been modified and reidentified in accordance with paragraph
(d)(2) of this AD.
Alternative Methods of Compliance
(h) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Los
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Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate. Operators shall submit their requests through an
appropriate FAA Principal Maintenance Inspector, who may add
comments and then send it to the Manager, Los Angeles ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
Special Flight Permits
(i) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
Incorporation by Reference
(j) The actions shall be done in accordance with McDonnell
Douglas MD-80 Service Bulletin MD80-32-276, dated March 31, 1995;
McDonnell Douglas MD-80 Service Bulletin MD80-32-276, Revision 1,
dated October 17, 1995; McDonnell Douglas MD-80 Service Bulletin
MD80-32-278, dated March 31, 1995; McDonnell Douglas MD-80 Service
Bulletin MD80-32-278, Revision 1, dated September 6, 1995; McDonnell
Douglas Service Bulletin DC9-32-289, dated March 7, 1996; McDonnell
Douglas Service Bulletin DC9-32-311, dated July 6, 1998; or
McDonnell Douglas Alert Service Bulletin DC9-32A311, Revision 1,
dated March 8, 1999; as applicable.
(1) The incorporation by reference of McDonnell Douglas Service
Bulletin DC9-32-311, dated July 6, 1998; or McDonnell Douglas Alert
Service Bulletin DC9-32A311, Revision 1, dated March 8, 1999; is
approved by the Director of the Federal Register in accordance with
5 U.S.C. 552(a) and 1 CFR part 51.
(2) The incorporation by reference of McDonnell Douglas MD-80
Service Bulletin MD80-32-276, dated March 31, 1995, McDonnell
Douglas MD-80 Service Bulletin MD80-32-276, Revision 1, dated
October 17, 1995; McDonnell Douglas MD-80 Service Bulletin MD80-32-
278, dated March 31, 1995; and McDonnell Douglas MD-80 Service
Bulletin MD80-32-278, Revision 1, dated September 6, 1995; was
approved previously by the Director of the Federal Register as of
February 26, 1996 (61 FR 2407, January 26, 1996).
(3) The incorporation by reference of McDonnell Douglas Service
Bulletin DC9-32-289, dated March 7, 1996, was approved previously by
the Director of the Federal Register as of November 14, 1996 (61 FR
53042, October 10, 1996).
(4) Copies may be obtained from Boeing Commercial Aircraft
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach,
California 90846. Copies may be inspected at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or
at the FAA, Transport Airplane Directorate, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood,
California; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
(k) This amendment becomes effective on November 12, 1999.
Issued in Renton, Washington, on September 28, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-25766 Filed 10-6-99; 8:45 am]
BILLING CODE 4910-13-U
